CN108048717A - Aluminum bronze lithium alloy with improved compression strength and toughness - Google Patents

Aluminum bronze lithium alloy with improved compression strength and toughness Download PDF

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CN108048717A
CN108048717A CN201810016958.8A CN201810016958A CN108048717A CN 108048717 A CN108048717 A CN 108048717A CN 201810016958 A CN201810016958 A CN 201810016958A CN 108048717 A CN108048717 A CN 108048717A
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yield stress
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A·丹尼路
G·普热
C·希格里
T·沃纳
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Constellium Issoire SAS
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Constellium France SAS
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent

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  • Heat Treatment Of Steel (AREA)
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Abstract

The present invention relates to the methods of manufacture rolled products made of acieral.The invention further relates to the rolled products obtained by this method, provide compression and stretch lower favourable compromise between mechanical strength and fracture toughness.The product of the present invention is especially suitable for manufacturing portion of upper airfoil covering.

Description

Aluminum bronze lithium alloy with improved compression strength and toughness
The application is the 201180065410.9 of entitled " the aluminum bronze lithium alloy with improved compression strength and toughness " The divisional application of number application for a patent for invention.Original application corresponds to International Application Serial No. PCT/FR2011/000659 applyings date as 2011 12 The moon 16, priority date are on December 20th, 2010.
Technical field
The present invention relates to aluminum bronze lithium alloy product, and more specifically it is designated specifically to such production of Aerospace Engineering Product, its manufacturing method and purposes.
Background technology
Rolled products are developed to manufacture high-strength parts made of aluminium alloy, and the component is designated specifically to navigate Empty aerospace industry.
At this point, the aluminium alloy containing lithium has been a great concern, because the density of aluminium can be reduced 3% and will by lithium Elasticity modulus increases by 6%, the lithium meter added in based on every weight percent.In order to which these alloys is allowed to be selected for aircraft, it Performance must reach the performance of the alloy being commonly used compared with other common characteristics, it is especially special in static mechanical strength Property (stretch and compressive yield stress, ultimate tensile strength) and damage tolerance characteristic (fracture toughness, fatigue crack autgmentability) Between compromise in terms of, these characteristics are typically contradiction.For some components such as upper surface of the airfoil, compression yield should Power is an essential characteristic.These mechanical properties should further preferably be stablized and have good thermal stability at any time, That is, the aging at a temperature of being not used significantly is modified.
These alloys must also with enough corrosion resistancies, can according to common method shape and with relatively low Residual stress is so as to be integrally machined.
United States Patent (USP) 5,032,359 describes the addition of a major class aluminum bronze lithium alloy, wherein magnesium and silver --- particularly exists Between 0.3 and 0.5 weight % --- make it possible increase mechanical strength.
United States Patent (USP) 5,455,003 describes the method for manufacturing Al-Cu-Li alloys, and the alloy is in cryogenic temperature Lower mechanical strength and fracture toughness with improvement, this is especially attributed to suitable machining deformation and tempering (revenu).This is specially The following composition of sharp special recommendation is in terms of weight percentage Cu=3.0-4.5, Li=0.7-1.1, Ag=0-0.6, Mg=0.3-0.6 and Zn=0-0.75.
United States Patent (USP) 7,438,772 is described comprising Cu as expressed in weight percent:3-5、Mg:0.5-2、Li:0.01- 0.9 alloy, the alloy are reduced due to the balance between fracture toughness and mechanical strength so it is not recommended that high level lithium makes With.
United States Patent (USP) 7,229,509 describes the alloy (weight %) comprising following component：(2.5-5.5)Cu、(0.1- 2.5) Li, (0.2-1.0) Mg, (0.2-0.8) Ag, (0.2-0.8) Mn, 0.4 maximum level Zr or other grain refiners such as Cr, Ti、Hf、Sc、V。
U.S. Patent application 2009/142222A1 describes the alloy (weight %) comprising following component：3.4 to 4.2% Cu, 0.9 to 1.4%Li, 0.3 to 0.7%Ag, 0.1 to 0.6%Mg, 0.2 to 0.8%Zn, 0.1 to 0.6%Mn and 0.01 to 0.6% at least one element for being used to control grain structure.This application also illustrates the manufacturing method of extruded product.
In the presence of the needs to the rolled products made of aluminum bronze lithium alloy, the product has to be changed compared with known product Kind characteristic, especially in static mechanical strength characteristic (particularly stretching and compressive yield stress) and damage tolerance characteristic (especially Fracture toughness, thermal stability, corrosion resistance and machining property) between compromise in terms of, while there is relatively low density.
In addition, also there are the needs of manufacturing method reliable to these products and economic.
The content of the invention
The first topic of the present invention is the method for manufacturing the rolled products based on aluminium alloy, wherein carrying out following behaviour successively Make：
A) bath of molten metal based on aluminium for including following component is prepared：Cu, 0.8 to 1.30 weight of 4.2 to 4.6 weight % Measure the Li of %, the Mg of 0.3 to 0.8 weight %, the Zr of 0.05 to 0.18 weight %, the Ag of 0.05 to 0.5 weight %, 0.0 to 0.5 The Mn of weight %, the at most Fe+Si of 0.20 weight %, the Zn less than 0.20 weight %, at least one are selected from Cr, Sc, Hf and Ti Element, if the amount of the element, --- its be chosen --- is：For Cr and Sc for 0.05 to 0.3 weight %, for Hf It is 0.01 to 0.15 weight % for 0.05 to 0.5 weight % and for Ti, other elements are at most each 0.05 weight % and total It is at most 0.15 weight % altogether, remaining is aluminium；
B) rolled slab is cast by the bath of molten metal；
C) by the rolled slab homogenize to reach 5 to 60 it is small when 450 DEG C and 550 DEG C of duration between temperature with And the temperature between preferably 480 DEG C and 530 DEG C；
D) by being kept above the temperature of 400 DEG C and preferably above 420 DEG C, the rolled slab is rolled into plate,
E) by the plate when progress solution treatment is 15 minutes small to 8 between 490 and 530 DEG C, and the product is quenched；
F) plate undergoes controlled stretching, wherein 2 to 3.5% and preferably 2.0 to 3.0% are permanently deformed to,
G) it is tempered, wherein the plate reaches between temperature between 130 and 170 DEG C and preferably 150 and 160 DEG C Temperature is small and when preferably 10 to 70 is small with 5 to 100,
On condition that the plate is not cold worked significantly between hot rolling d) and solution treatment e), especially by cold It rolls.
Second theme of the present invention is can be 8 to 50mm by the thickness that the method for the present invention obtains and not weigh predominantly There are the rolled products of the grain structure of crystallization at least one following characteristics to combine at middle thickness：
(i) thickness for 8 to 15mm --- for 300mm wide and the thick CCT test samples of 6.35mm, in middle thickness Place, stretching yield stress Rp0.2(L) >=600MPa and preferred Rp0.2(L)≥610MPa；Compressive yield stress Rp0.2(L)≥ 620MPa and preferred Rp0.2(L) >=630MPa and fracture toughness are so that K1C(L-T) >=28MPa √ m and preferred K1C(L-T) >=32MPa √ m and/or Kapp(L-T) >=73MPa √ m and preferred Kapp(L-T) >=79MPa √ m,
(ii) thickness for 8 to 15mm --- for 300mm wide and the thick CCT test samples of 6.35mm, in middle thickness Place, stretching yield stress Rp0.2(L) >=630MPa and preferred Rp0.2(L)≥640MPa；Compressive yield stress Rp0.2(L)≥ 640MPa and preferred Rp0.2(L) >=650MPa and fracture toughness are so that K1C(L-T) >=26MPa √ m and preferred K1C(L-T) >=30MPa √ m and/or Kapp(L-T) >=63MPa √ m and preferred Kapp(L-T) >=69MPa √ m,
(iii) thickness for 15 to 50mm, at middle thickness, stretching yield stress Rp0.2(L) >=610MPa and excellent Select Rp0.2(L)≥620MPa；Compressive yield stress Rp0.2(L) >=620MPa and preferred Rp0.2(L) >=630MPa and fracture toughness K1C(L-T) >=22MPa √ m and preferred K1C(L-T) >=24MPa √ m,
(iv) thickness for 15 to 50mm, at middle thickness, stretching yield stress Rp0.2(L) >=580MPa and preferably Rp0.2(L)≥590MPa；Compressive yield stress Rp0.2(L) >=600MPa and preferred Rp0.2(L) >=610MPa and fracture toughness K1C (L-T) >=24MPa √ m and preferred K1C(L-T)≥26MPa√m。
Another theme of the present invention is the aircraft structural component of the product comprising the present invention, preferably portion of upper airfoil covering.
It is the use that the product of the present invention or the structural detail of the present invention are used for aeronautical engineering that the present invention, which also has another theme, On the way.
Description of the drawings
Fig. 1：Tempering curve and tangent line PNThe example of the measure of slope.
Fig. 2：Compressive yield stress and stretching yield stress are with the variation of permanent deformation during controlled stretch.
Fig. 3：The compressive yield stress and K of N ° 2 to N ° 5 of alloy in embodiment 2appCharacteristic compromise between fracture toughness.
Specific embodiment
Unless otherwise stated, the statement of the chemical composition of all about alloy is with the weight hundred of the total weight based on alloy Divide than representing.Statement 1.4Cu means to be multiplied by 1.4 with the copper content that weight % is represented.The name of alloy and those skilled in the art Known Aluminum Association (The Aluminium Association) rule is consistent.Density depends on forming and passing through calculating really Determine rather than determined by the method for weight measurement.The step of calculating of numerical value meets Aluminum Association it is recorded in " Aluminum The 2-12 pages and 2-13 pages of Standards and Data ".The definition of metallurgical state is shown in European standard EN 515.
Stretch static mechanical feature, that is, ultimate tensile strength Rm, 0.2% extend when conventional yield stress Rp0.2 And elongation at break A% is measured by the extension test according to standard EN ISO 6892-1, sampling and measurement direction are by standard EN 485-1 are provided.
Compressive yield stress is measured according to standard ASTM E9 under 0.2% compression.
Stress intensity factor (KQ) determined according to standard ASTM E 399.Standard ASTM E 399, which are provided, can determine KQWhether For K1CVirtual value standard.For given test sample geometry, the obtained K of different materialsQValue can mutually compare, So that the yield stress of material has same order.
The coordinate diagram --- referred to as R-curve --- of stress intensity On Crack Propagation is measured according to standard ASTM E561.Face Boundary's stress strength factor KC--- intensity factor for namely making crackle unstable --- is calculated by R-curve.Stress intensity factor KCOAlso by single load (charge monotone) start Initial crack length being attributed to critical load calculate. The two values are calculated to the sample of regulation shape.KappRepresent the K for corresponding to the sample for being used for carrying out R-curve testCOThe factor.
Unless specified otherwise herein, using the definition of standard EN 12258.
" structural detail " of the mechanical structure of this paper refers to a kind of mechanical part, for the mechanical part its it is static and/ Or dynamic mechanically characteristic is especially important for the performance of the structure, and for the mechanical part usually regulation or carry out structure Analysis.They are typically such element, and failure may endanger the structure, its operator, its user or other peaces Entirely.For aircraft, these structural details are included such as lower component, composition fuselage (such as fuselage skin (fuselage Skin), longeron (stringer), bulkhead (bulkhead), perimeter frame (circumferential frames)), wing (example Such as top or portion of lower airfoil covering, longeron or stringer (stiffener), rib (rib) and spar (spar)) and it is special The tail gear and joist (floor beam), seat rail (seat not being made of horizontal and vertical stabilizer ) and door track.
According to the present invention, selected aluminium alloy class --- it contains specific and lithium, copper, magnesium, silver and zirconium of critical quantity --- It can prepare under specific conversion condition and compromise between the fracture toughness with improvement, stretching yield stress and compressive yield stress The rolled products of property.
Unexpectedly, the present inventors have noted that --- especially in hot-working and pass through restrained stretching and eliminate stress (d é Tentionnement during) --- it can be answered by selecting specific conversion process parameter to improve the compression yield of these alloys Power.
The copper content of product of the present invention is between 4.2 and 4.6 weight %.In a favourable embodiment of the invention In, copper content is at least 4.3 weight %.It is preferred that the maximum copper content of 4.4 weight %.
The lithium content of product of the present invention is located at 0.8 weight % or 0.80 weight % and 1.30 weight % and preferably 1.15 weights Between amount %.Advantageously, lithium content is at least 0.85 weight %.It is preferred that the maximum lithium content of 0.95 weight %.
The copper content and increase of lithium content helps to improve static mechanical strength --- to a lesser extent ---；But It is, because copper especially has adverse effect density, copper content to be preferably defined to preferred maximum.Increase lithium content pair Density has favorable influence；But the present inventors have noted that for alloy of the invention, in one embodiment, scope exists Preferred lithium content between 0.85 weight % and 0.95 weight % helps to improve mechanical strength (stretching yield stress and compression Yield stress) compromise between fracture toughness, in addition, peak value or close to peak value obtain for tempering fracture toughness more It is high.In another embodiment --- wherein make compressive yield stress and low-density preferential to obtain relatively low toughness, it is excellent The lithium content scope of choosing between 1.10 weight % and 1.20 weight %, while preferred content of magnesium scope in 0.50 weight % or It is preferred that between 0.53 weight % and 0.70 weight % or preferably 0.65 weight %.
The content of magnesium of product of the present invention is between 0.3 weight % or 0.30 weight % and 0.8 or 0.80 weight %.It is preferred that Ground, content of magnesium is at least 0.40 weight % or even 0.45 weight %, the content can improve static mechanical strength and fracture simultaneously Toughness.The present inventors have noted that scope is in 0.50 weight % or preferably 0.53 weight % and 0.70 weight % or preferably 0.65 weight Measure content of magnesium between % and scope between 0.85 weight % and 1.15 weight % and preferably in 0.85 weight % and The combination of lithium content between 0.95 weight % can cause particularly advantageous mechanical strength (stretching and compressive yield stress) and break The compromise between toughness is split, while acceptable failure rate is kept during conversion, and therefore generates this manufacturing method and makes us full Meaning ground reliability.
Zirconium content between 0.05 weight % and 0.18 weight % and preferably 0.08 weight % and 0.14 weight % it Between.In a favourable embodiment of the invention, zirconium content is at least 0.11 weight %.
Manganese content is between 0.0 and 0.5 weight %.In a favourable embodiment of the invention, manganese content 0.2 And 0.4 between weight %.In another embodiment of the invention, manganese content is less than 0.1 weight % and preferably shorter than 0.05 Weight %, this product that can obtain the method by the present invention reduce the amount of insoluble metal phase and further improve damage Hinder tolerance limit.
Silver content is between 0.05 weight % and 0.5 weight %.In a favourable embodiment of the invention, silver contains It measures between 0.10 weight % and 0.40 weight %.The addition of silver helps to improve the product of the method acquisition by the present invention The compromise of mechanical property.
The summation of iron content and silicone content is at most 0.20 weight %.Preferably, iron and silicone content are at most each 0.08 Weight %.In a favourable embodiment of the invention, the content of iron and silicon is at most 0.06 weight % and 0.04 weight respectively Measure %.Iron and silicone content controlled and limit help to improve the compromise between mechanical strength and damage tolerance.
The alloy also containing it is at least one contribute to control crystallite dimension element, the element be selected from Cr, Sc, Hf and Ti, if the amount of the element, --- it is chosen --- is：It is 0.05 to 0.3 weight % for Cr and Sc, is for Hf 0.05 to 0.5 weight % and for Ti be 0.01 to 0.15 weight %.Preferably, selection is added between 0.01 and 0.10 weight % Titanium and limit the content of Cr, Sc and Hf as 0.05 weight % of maximum because these elements can especially have to density it is unfavorable Influence and its addition only further aid the acquisition predominantly structure (if necessary) of recrystallization.
Zinc is unwanted impurity, this is particularly as its effect to alloy density.Zn content is excellent less than 0.20 weight % The weight % of the weight % and more preferable Zn of selection of land Zn≤0.15≤0.05.Zn content is advantageously lower than 0.04 weight %.
The content of alloying element can be selected to minimize density.Preferably, it will help increase the element (example of density Such as Cu, Zn, Mn and Ag) addition minimize and will be helpful to reduce the element (such as Li and Mg) of density and maximize, so as to real Now it is less than 2.73g/cm3And preferably smaller than 2.70g/cm3Density.
The manufacturing method of the product of the present invention rolls including preparing, casting, homogenizing, at a temperature of higher than 400 DEG C, is solid Molten the step of handling, quench, being stretched between 2 and 3.5% and being tempered.
In the first step, bath of molten metal is prepared to obtain the aluminium alloy formed according to the present invention.
Then the bath of molten metal is cast to the shape of rolled slab.
Then the rolled slab is homogenized to realize the temperature between 450 DEG C and 550 DEG C of the duration when 5 to 60 is small And the temperature between preferably 480 DEG C and 530 DEG C.The homogenize process can carry out in one or multi-step.
After homogenization, the rolled slab is usually cooled to room temperature, the preheating then prepared into behavior hot rolling.Pre-add The purpose of heat is to realize following temperature, and the temperature to keep at least 400 DEG C of temperature and excellent in the hot rolling The temperature of at least 420 DEG C of choosing.If temperature declines excessive in course of hot rolling, resuperheat can be carried out.Hot rolling is carried out until thickness It is preferred that the scope between 8 and 50mm and between preferably 12 and 40mm.
Without being significantly cold worked between hot rolling and solution treatment, especially by cold rolling.It is in fact, such cold Recrystallizationization structure will likely be generated by rolling step, and the structure is undesirable within the scope of the present invention.It is significantly cold to add Work is generally at least about 5% or 10% deformation.
Then the product so obtained is subjected to solution treatment by being heat-treated, the heat treatment can be achieved 15 minutes to 8 The temperature of scope, is then usually quenched with room temperature water or preferably with cold water between the duration 490 of hour and 530 DEG C.
Selected ingredient --- particularly zirconium content --- and transformation range --- be particularly hot processing temperature and There is no cold working before solution treatment --- combination may be such that be mainly recrystallization grain structure." predominantly The grain structure of recrystallization " means to have at middle thickness more than 70% and the crystalline substance of preferably greater than 85% recrystallization The content of kernel structure.
Then the product undergoes controlled stretching, is permanently deformed to 2 to 3.5% and preferably 2.0% to 3.0%.Tool The controlled stretching of about 2.5% maximum permanent deformation is preferred.Unexpectedly, the present inventors have noted that in controlled drawing During stretching, with the increase of permanent deformation, compressive yield stress reduces stretching yield stress simultaneously to be increased under these conditions. Accordingly, there exist the optimal permanent deformation by controlled stretch, the compressive yield stress that acquisition can be made higher while keep enough Stretching yield stress.Advantageously, selection passes through the permanent deformation of controlled stretch to obtain at least equal to stretching yield stress Compressive yield stress.Unexpectedly, the inventors have further noted that permanent set to the effect of compressive yield stress to rolling Product has specificity；The test of extruded product is shown, such effect is not observed in this case.
Known steps can be optionally after solution treatment and quenching and in controlled drawing as rolled, flattening, aligning or shaping It is carried out before or after stretching.In one embodiment of the invention, at least 7% and preferably at least 9% and at most 15% Cold rolling step carry out after solution treatment and quenching and before controlled stretch.But particularly contemplate the additional cold rolling The cost of step is advantageously directly realized by controlled stretch after solution treatment and quenching in another embodiment.
Be tempered, wherein product 5 to 100 it is small and realize when preferably 10 to 70 is small between 130 and 170 DEG C with And the temperature range preferably between 150 and 160 DEG C.Tempering can carry out in one or multi-step.
It is known for the alloy of structure hardening (durcissement structural) such as Al-Cu-Li alloys, bend It takes stress and increases to the maximum for being referred to as hardening peak value or " peak value " with the duration of the tempering at a temperature of given, so Afterwards as tempering time reduces.Within the scope of the present invention, tempering curve is yield stress with the tempering equivalent time at 155 DEG C Variation.One example of tempering curve is presented in Fig. 1.Within the scope of the present invention, by measuring tangent line of the tempering curve in N points Slope PNTo determine the N of tempering curve points --- 155 DEG C of equivalent time tNAnd yield stress Rp0.2(N)--- whether approach Peak value.Within the scope of the present invention, if slope PNAbsolute value be at most 3MPa/h, then it is assumed that the surrender of the N points of tempering curve Stress is close to the yield stress of peak value.As shown in Figure 1, it is P to owe tempering (sous-revenu) stateNFor the state and mistake of positive number (sur-revenu) state of tempering is PNIt is the state of negative.
In order to obtain the P of the N points for owing the curve in annealed stripNApproximation, can measure by N points and by it The slope on the right of preceding N-1 points, N-1 points are for time tN-1<tNIt obtains and there is Rp0.2(N-1)Yield stress；This obtains PN ≈(Rp0.2(N)-Rp0.2(N-1))/(tN–tN-1).In theory, t is worked asN-1Tend to tNWhen obtain PNExact value.But if tN– tN-1Difference it is small, then the variation of yield stress may be inapparent and described value is inaccurate.The present inventors have noted that work as tN–tN-1Difference be located at 2 and 20 it is small when between and at preferably from about 3 hours, then usually obtain PNSatisfactory approximation.
In 155 DEG C of equivalent time tiIt is limited by following formula：
Wherein T (with Kelvinometer) is the instant treatment temperature of metal, as time t (in hours) changes, and TrefTo be fixed on the reference temperature(TR) of 428K.tiIt is represented with hour.The activation energy of the diffusion of constant Q/R=16,400K from Cu, Q values=136,100J/mol is used for it.
It stretches or compressive yield stress may be used to determine the state that is tempered and whether can realize close to peak value；But the result It is not necessarily the same.Within the scope of the invention, it is preferable to use the values of compressive yield stress to optimize tempering.
Typically for the alloy of Al-Cu-Li types, it will be apparent that owe annealed strip and correspond to static mechanical strength (Rp0.2Rm) the compromise ratio between damage tolerance (fracture toughness, fatigue crack autgmentability) be in peak value and --- more Needless to say --- it more attracts people's attention more than peak value.But the present inventors have noted that the state close to peak value can both provide static machine Good compromise between tool intensity and damage tolerance, and the performance in terms of corrosion resistance and thermal stability can be improved.
In addition, utilize the stability that industrial process can be improved close to peak state：The variation of tempered condition causes acquisition The slight change of characteristic.
Therefore it is advantageous that carry out close to the peak value of compressive yield stress substantially owe tempering state, i.e. the time and The condition equivalence of temperature is in the state for substantially owing tempering of the N points of the tempering curve compressed at 155 DEG C, so that tempering curve There is the slope P represented with MPa/h in the tangent line of the pointN, make -1<PN≤ 3 and preferably -0.5<PN≤2.3。
The rolled products obtained by the method for the present invention are for scope for thickness between 8 and 50mm, in middle thickness There is at least one following property combination at degree：
(i) thickness for 8 to 15mm --- for 300mm wide and the thick CCT test samples of 6.35mm, in middle thickness Place, stretching yield stress Rp0.2(L) >=600MPa and preferred Rp0.2(L)≥610MPa；Compressive yield stress Rp0.2(L)≥ 620MPa and preferred Rp0.2(L) >=630MPa and fracture toughness are so that K1C(L-T) >=28MPa √ m and preferred K1C(L-T) >=32MPa √ m and/or Kapp(L-T) >=73MPa √ m and preferred Kapp(L-T) >=79MPa √ m,
(ii) thickness for 8 to 15mm --- for 300mm wide and the thick CCT test samples of 6.35mm, in middle thickness Place, stretching yield stress Rp0.2(L) >=630MPa and preferred Rp0.2(L)≥640MPa；Compressive yield stress Rp0.2(L)≥ 640MPa and preferred Rp0.2(L) >=650MPa and fracture toughness are so that K1C(L-T) >=26MPa √ m and preferred K1C(L-T) >=30MPa √ m and/or Kapp(L-T) >=63MPa √ m and preferred Kapp(L-T) >=69MPa √ m,
(iii) thickness for 15 to 50mm, at middle thickness, stretching yield stress Rp0.2(L) >=610MPa and excellent Select Rp0.2(L)≥620MPa；Compressive yield stress Rp0.2(L) >=620MPa and preferred Rp0.2(L) >=630MPa and fracture toughness K1C(L-T) >=22MPa √ m and preferred K1C(L-T) >=24MPa √ m,
(iv) thickness for 15 to 50mm, at middle thickness, stretching yield stress Rp0.2(L) >=600MPa and preferably Rp0.2(L)≥610MPa；Compressive yield stress Rp0.2(L) >=580MPa and preferred Rp0.2(L) >=590MPa and fracture toughness K1C (L-T) >=24MPa √ m and preferred K1C(L-T)≥26MPa√m。
The aircraft structural component of the present invention includes the product of the present invention.Preferred aircraft structural component covers for portion of upper airfoil Skin.
It includes the product of at least one present invention or aeronautical engineering is used in particular for by the structural detail of this product manufacturing Purposes is favourable.The product of the present invention is particularly advantageous for manufacturing the portion of upper airfoil covering of aircraft.
These aspects and other aspects of the present invention use the example below illustrative and non-limiting embodiment carries out It is explained in more detail.
Embodiment
Embodiment 1
In this embodiment, the plate that the section made of the alloy of the method from the present invention is 406x1520mm is cast Base, composition are given in Table 1.
Table 1, N ° 1 of alloy with forming of counting of weight % and density
The slab is homogenized at about 500 DEG C about 20 it is small when.By slab hot rolling at a temperature of more than 445 DEG C To obtain plate of the thickness as 25mm.Plate is carried out at about 510 DEG C solution treatment 5 it is small when, then with 20 DEG C of water quenching.Then By the permanent elongation of scope between plate stretching 2% and 6%.
By plate at 155 DEG C for the stretching of 2 and 3% carry out single step tempering 40 it is small when, for 4% stretching carry out it is 30 small When and for 6% stretching carry out 20 it is small when, which to obtain in peak value or the stretching yield stress close to peak value And compressive yield stress.It is sampled at middle thickness, the static mechanical characteristic under stretching and compress with measurement, together with fracture toughness KQ.For the thickness of width and B=20mm of the test sample with W=40mm of fracture toughness measurement.Measurements made according to Standard ASTM E399 are effective.As a result it is given in Table 2.
The structure of the plate of acquisition predominantly recrystallization.The ratio of the grain structure of recrystallization at middle thickness For 90%.
Table 2, the mechanical property obtained for different plates.
Fig. 2 shows the letter of stretching yield stress and compressive yield stress as the permanent elongation during controlled stretch Several variations.For the permanent elongation in drawing process between scope 2 and 3.5%, compressive yield stress and stretching are obtained Favourable compromise between yield stress.Therefore under these conditions, compressive yield stress is higher than stretching yield stress, stretches and bends It takes stress and is kept above 620MPa.
Embodiment 2
In this embodiment, the slab that multiple sections are 120X 80mm is cast, composition is given in Table 3.
Table 3 is cast into the Al-Cu-Li alloys of slab form with forming of counting of weight % and density
By the slab by 500 DEG C 8 it is small when then at 510 DEG C 12 it is small when two-step pretreatment homogenize, then Carry out surface mechanical processing.After homogenization, by slab hot rolling to obtain plate of the thickness as 9.4mm, if temperature is brought down below 400 DEG C, then carry out intermediate reheating.At about 510 DEG C by plate carry out solution treatment 5 it is small when, quenched with cold water and stretch 3% Permanent elongation.
The structure of the plate of acquisition predominantly recrystallization.The ratio of the grain structure of recrystallization at middle thickness For 90%.
At 155 DEG C by plate into line range when 15 and 50 are small between tempering.Sampling and measuring is stretched, pressed at middle thickness Static mechanical characteristic and fracture toughness K under contractingQ.For fracture toughness measurement test sample with W=425mm width and The thickness of B=8mm.K1CValidity criteria for some samples be meet.Fracture toughness measurement is also 300mm and thickness in width It spends on the CCT samples for 6.35mm and obtains.The result of gained is given in Table 4.
Table 4, the mechanical property obtained for different plates
Fig. 3 shows compressive yield stress and fracture toughness KappBetween the compromise that obtains.
Preferred composition (N ° 3 of alloy) and the method for the present invention --- when tempering 50 is small especially at 155 DEG C, it is tempered from heat Best from the perspective of stability --- combination give particularly advantageous compressive yield stress, stretching yield stress Compromise between fracture toughness.
Embodiment 3
In this embodiment, the plate that the section made of the alloy of the method from the present invention is 406x1525mm is cast Base, composition are given in Table 5.
N ° 6 of 5. alloy of table with forming of counting of weight % and density
Alloy Si Fe Cu Mn Mg Zn Ag Li Zr Ti Density (g/cm3)
N°6 0.02 0.03 4.3 - 0.58 ＜ 0.01 0.34 0.88 0.13 0.04 2.714
The slab is homogenized at about 500 DEG C about 30 it is small when.By slab hot rolling at a temperature of more than 400 DEG C To obtain plate of the thickness as 25mm.Plate is carried out at about 510 DEG C solution treatment 5 it is small when, then with 20 DEG C of water quenching.Then By the permanent elongation of plate stretching 2% or 3%.
Plate is carried out at 155 DEG C single step be tempered 10 hours to 30 it is small when.It is sampled at middle thickness, is stretched and pressed with measurement Static mechanical characteristic under contracting, together with fracture toughness KQ.There is the width of W=40mm for the test sample of fracture toughness measurement With the thickness of B=20mm.Measurements made is effective according to standard ASTM E399.As a result it is given in Table 6.
The structure of the plate of acquisition predominantly recrystallization.The ratio of the grain structure of recrystallization at middle thickness For 90%.
Table 6, the mechanical property obtained for different plates

Claims (13)

1. the method for the rolled products based on aluminium alloy is manufactured, wherein follow the steps below successively,
A) bath of molten metal based on aluminium for including following component is prepared：Cu, 0.85 to 0.95 weight of 4.2 to 4.6 weight % Measure the Li of %, the Mg of 0.5 to 0.7 weight %, the Zr of 0.05 to 0.18 weight %, the Ag of 0.05 to 0.5 weight %, less than 0.1 The Mn of weight %, the at most Fe+Si of 0.20 weight %, the Zn less than 0.20 weight %, at least one are selected from Cr, Sc, Hf and Ti Element, if the amount of the element, --- its be chosen --- is：For Cr and Sc for 0.05 to 0.3 weight %, for Hf It is 0.01 to 0.15 weight % for 0.05 to 0.5 weight % and for Ti, other elements are at most each 0.05 weight % and total It is at most 0.15 weight % altogether, remaining is aluminium；
B) rolled slab is cast by the bath of molten metal；
C) by the rolled slab homogenize to reach 5 to 60 it is small when 450 DEG C and 550 DEG C of duration between temperature and excellent Select the temperature between 480 DEG C and 530 DEG C；
D) by being kept above the temperature of 400 DEG C and preferably above 420 DEG C, the rolled slab is rolled into plate,
E) by the plate when progress solution treatment is 15 minutes small to 8 between 490 and 530 DEG C, and the product is quenched；
F) plate undergoes controlled stretching, wherein 2 to 3.5% and preferably 2.0 to 3.0% are permanently deformed to,
G) it is tempered, wherein the plate reaches the temperature between temperature between 130 and 170 DEG C and preferably 150 and 160 DEG C It is small and when preferably 10 to 70 is small with 5 to 100,
On condition that the plate is not cold worked significantly between hot rolling d) and solution treatment e), especially by cold rolling.
2. the method according to claim 1, wherein copper content are 4.3 weight % to 4.4 weight %.
3. according to the method for claim 1 or claim 2, the wherein content of Li is up to 1.15 weight %, preferably 0.85 to 0.95 weight %.
4. according to the method for claim 1 or claim 2, wherein Li contents are 1.10 to 1.20 weight %.
5. according to the method for any one of claim 3 to 4, the wherein content of Mg is 0.50 to 0.70 weight %, is preferably 0.53 to 0.65 weight %.
6. according to the method for any one of claim 1 to 5, wherein Mn contents are less than 0.05 weight %.
7. according to the method for any one of claim 1 to 6, wherein
The content of Fe and Si each be at most 0.08 weight % and/or
Ti contents for the content of 0.01 to 0.10 weight % and Cr, Sc and Hf be at most 0.05 weight % and/or
Zn contents are at most 0.15 weight %, preferably up to 0.05 weight %.
8. according to the method for any one of claim 1 to 7, wherein by the permanent deformation selected as of controlled stretch can obtain to It is equal to the compressive yield stress of stretching yield stress less.
9. according to the method for any one of claim 1 to 8, wherein controlled stretch is directly realized by after solution treatment and quenching.
10. according to the method for any one of claim 1 to 9, wherein tempering is the deficient tempering close to compressive yield stress peak value.
It is 11. between 8 and 50mm and main by the thickness range obtained according to the method for any one of claims 1 to 10 For the rolled products of the grain structure of recrystallization, there is at least one following property combination at middle thickness：
(i) thickness for 8 to 15mm --- for 300mm wide and the thick CCT test samples of 6.35mm, at middle thickness, draw Stretch yield stress Rp0.2(L) >=600MPa and preferred Rp0.2(L)≥610MPa；Compressive yield stress Rp0.2(L) >=620MPa with And preferably Rp0.2(L) >=630MPa and fracture toughness are so that K1C(L-T) >=28MPa √ m and preferred K1C(L-T)≥32MPa √ m and/or Kapp(L-T) >=73MPa √ m and preferred Kapp(L-T) >=79MPa √ m,
(ii) thickness for 8 to 15mm --- for 300mm wide and the thick CCT test samples of 6.35mm, at middle thickness, draw Stretch yield stress Rp0.2(L) >=630MPa and preferred Rp0.2(L)≥640MPa；Compressive yield stress Rp0.2(L) >=640MPa with And preferably Rp0.2(L) >=650MPa and fracture toughness are so that K1C(L-T) >=26MPa √ m and preferred K1C(L-T)≥30MPa √ m and/or Kapp(L-T) >=63MPa √ m and preferred Kapp(L-T) >=69MPa √ m,
(iii) thickness for 15 to 50mm, at middle thickness, stretching yield stress Rp0.2(L) >=610MPa and preferred Rp0.2 (L)≥620MPa；Compressive yield stress Rp0.2(L) >=620MPa and preferred Rp0.2(L) >=630MPa and fracture toughness K1C(L- T) >=22MPa √ m and preferred K1C(L-T) >=24MPa √ m,
(iv) thickness for 15 to 50mm, at middle thickness, stretching yield stress Rp0.2(L) >=580MPa and preferred Rp0.2 (L)≥590MPa；Compressive yield stress Rp0.2(L) >=600MPa and preferred Rp0.2(L) >=610MPa and fracture toughness K1C(L- T) >=24MPa √ m and preferred K1C(L-T)≥26MPa√m。
12. aircraft structural component, preferably portion of upper airfoil covering, include product according to claim 11.
13. product according to claim 11 or structural detail according to claim 11 are used for the purposes of aeronautical engineering.
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